控制二次流发展的前伸小圆角端区流动控制机理(英文)  

The Mechanism of Control the Development of End Wall Secondary Flow by Using Protrusive Small Rounded on the Leading Edge

作　　者：王松涛[1] 罗磊[1] 迟重然[1,2] 卢少鹏[1] 温风波[1] 刘轶[1] 

机构地区：[1]哈尔滨工业大学能源科学与工程学院,哈尔滨150001 [2]清华大学热能工程系,北京100084

出　　处：《科学技术与工程》2013年第9期2437-2440,2447,共5页Science Technology and Engineering

摘　　要：基于哈尔滨工业大学自主开发的带冷气叶片气动网格自动生成技术,通过Ansys公司下的CFX软件,对国产某型民用航空发动机高压涡轮第一级动叶进行设计。设计中采用了一种新型控制二次流发展的叶形,使用特殊前缘参数化设计方法。具体操作为叶片根部叶形前缘前伸,前缘修小圆,在前缘吸力面位置局部内凹,并沿叶高一定范围内进行光滑过渡,即形成根部区域修型,其他区域不变的新叶形。研究表明:采用此方法能够有效的降低由于叶片前缘马蹄涡造成的通道涡等涡系的尺度及强度,从而减少气动损失。Based on a self-program of automatic generated grid technology on aerodynamic blade with cooling air developed by Harbin Institute of Technology, the first rotor blade in high-pressure turbine of domestic civil avia- tion engine has been designed by using CFX software of Ansys Company. The design introduces a new blade which can control the second flow by using leading edge parametric design method. Specific operations for the blade con- tain protrusive, a small rounded as well as reversal curvature in front of the blade root, and in the rest of the blade height, the blade has no change. The research shows that using this new technology can reduce the strength and the scale of the passage vortex which caused by the horseshoe vortex on the Leading Edge so as to reduce the aerodynamic loss.

关 键 词：高压涡轮 前伸 小圆 内凹 通道涡 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]